MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 100,000 Max Cl/Cd: 53.1 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh32-il-100000-n5.txt Download as CSV file: xf-mh32-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4284 0.11183 0.10663 -0.0194 1.0000 0.0216
-9.750 -0.4253 0.10795 0.10280 -0.0208 1.0000 0.0202
-9.500 -0.4239 0.10374 0.09863 -0.0225 1.0000 0.0186
-9.000 -0.4212 0.09442 0.08940 -0.0280 1.0000 0.0153
-8.750 -0.4211 0.09042 0.08545 -0.0292 1.0000 0.0150
-8.500 -0.4205 0.08687 0.08196 -0.0304 1.0000 0.0147
-8.250 -0.4219 0.08297 0.07813 -0.0320 1.0000 0.0145
-8.000 -0.4242 0.07933 0.07457 -0.0334 1.0000 0.0143
-7.750 -0.4300 0.07560 0.07092 -0.0349 1.0000 0.0141
-7.500 -0.4357 0.07169 0.06709 -0.0371 1.0000 0.0139
-7.250 -0.4402 0.06697 0.06241 -0.0401 1.0000 0.0137
-7.000 -0.4434 0.06270 0.05814 -0.0417 1.0000 0.0134
-6.750 -0.4469 0.05815 0.05354 -0.0428 1.0000 0.0133
-6.500 -0.4486 0.05404 0.04933 -0.0429 1.0000 0.0131
-6.250 -0.4485 0.04990 0.04502 -0.0425 1.0000 0.0128
-6.000 -0.4457 0.04567 0.04054 -0.0420 1.0000 0.0127
-5.750 -0.4393 0.04163 0.03618 -0.0413 1.0000 0.0126
-5.500 -0.4293 0.03783 0.03198 -0.0405 1.0000 0.0128
-5.250 -0.4157 0.03443 0.02810 -0.0395 1.0000 0.0138
-5.000 -0.3834 0.03102 0.02398 -0.0413 0.9954 0.0150
-4.750 -0.3528 0.02748 0.01985 -0.0430 0.9907 0.0164
-4.500 -0.3205 0.02496 0.01690 -0.0444 0.9860 0.0173
-4.250 -0.2858 0.02288 0.01447 -0.0458 0.9821 0.0187
-4.000 -0.2544 0.02119 0.01246 -0.0464 0.9767 0.0205
-3.750 -0.2202 0.02001 0.01102 -0.0475 0.9718 0.0249
-3.500 -0.1870 0.01863 0.00959 -0.0489 0.9673 0.0319
-3.250 -0.1557 0.01758 0.00842 -0.0495 0.9609 0.0485
-3.000 -0.1210 0.01635 0.00745 -0.0512 0.9564 0.0995
-2.750 -0.0914 0.01536 0.00700 -0.0521 0.9497 0.2195
-2.500 -0.0585 0.01453 0.00674 -0.0535 0.9442 0.3737
-2.250 -0.0282 0.01389 0.00655 -0.0540 0.9379 0.5211
-2.000 0.0010 0.01340 0.00646 -0.0537 0.9313 0.6567
-1.750 0.0300 0.01307 0.00638 -0.0529 0.9246 0.7742
-1.500 0.0704 0.01284 0.00623 -0.0543 0.9192 0.8863
-1.250 0.1346 0.01265 0.00585 -0.0613 0.9169 0.9745
-1.000 0.1766 0.01259 0.00559 -0.0643 0.9093 1.0000
-0.750 0.2104 0.01253 0.00537 -0.0654 0.9010 1.0000
-0.500 0.2374 0.01252 0.00521 -0.0652 0.8896 1.0000
-0.250 0.2648 0.01251 0.00508 -0.0650 0.8783 1.0000
0.000 0.2925 0.01250 0.00497 -0.0648 0.8669 1.0000
0.250 0.3200 0.01248 0.00486 -0.0645 0.8553 1.0000
0.500 0.3471 0.01247 0.00476 -0.0641 0.8430 1.0000
0.750 0.3736 0.01246 0.00468 -0.0635 0.8296 1.0000
1.000 0.3995 0.01245 0.00462 -0.0629 0.8150 1.0000
1.250 0.4254 0.01245 0.00457 -0.0621 0.7994 1.0000
1.500 0.4514 0.01246 0.00454 -0.0614 0.7831 1.0000
1.750 0.4777 0.01246 0.00449 -0.0608 0.7664 1.0000
2.000 0.5034 0.01250 0.00449 -0.0600 0.7480 1.0000
2.250 0.5291 0.01255 0.00450 -0.0593 0.7286 1.0000
2.500 0.5550 0.01262 0.00452 -0.0585 0.7087 1.0000
2.750 0.5805 0.01272 0.00462 -0.0578 0.6869 1.0000
3.000 0.6059 0.01284 0.00470 -0.0570 0.6641 1.0000
3.250 0.6312 0.01300 0.00480 -0.0562 0.6406 1.0000
3.500 0.6562 0.01320 0.00494 -0.0554 0.6158 1.0000
3.750 0.6809 0.01343 0.00516 -0.0546 0.5899 1.0000
4.000 0.7053 0.01369 0.00537 -0.0537 0.5631 1.0000
4.250 0.7294 0.01399 0.00562 -0.0529 0.5356 1.0000
4.500 0.7531 0.01431 0.00590 -0.0520 0.5070 1.0000
4.750 0.7766 0.01467 0.00622 -0.0511 0.4776 1.0000
5.000 0.7997 0.01506 0.00662 -0.0502 0.4471 1.0000
5.250 0.8225 0.01549 0.00701 -0.0492 0.4160 1.0000
5.500 0.8448 0.01597 0.00744 -0.0483 0.3843 1.0000
5.750 0.8668 0.01648 0.00792 -0.0473 0.3519 1.0000
6.000 0.8883 0.01704 0.00844 -0.0463 0.3193 1.0000
6.250 0.9093 0.01767 0.00901 -0.0453 0.2877 1.0000
6.500 0.9301 0.01833 0.00971 -0.0443 0.2554 1.0000
6.750 0.9503 0.01906 0.01040 -0.0432 0.2239 1.0000
7.000 0.9698 0.01987 0.01115 -0.0421 0.1933 1.0000
7.250 0.9889 0.02073 0.01196 -0.0410 0.1615 1.0000
7.500 1.0072 0.02169 0.01286 -0.0398 0.1310 1.0000
7.750 1.0245 0.02277 0.01386 -0.0386 0.1031 1.0000
8.000 1.0412 0.02393 0.01501 -0.0372 0.0804 1.0000
8.250 1.0555 0.02534 0.01639 -0.0355 0.0638 1.0000
8.500 1.0691 0.02680 0.01785 -0.0338 0.0489 1.0000
8.750 1.0799 0.02849 0.01965 -0.0318 0.0392 1.0000
9.000 1.0925 0.02995 0.02127 -0.0300 0.0304 1.0000
9.250 1.1006 0.03186 0.02334 -0.0276 0.0254 1.0000
9.500 1.1092 0.03350 0.02509 -0.0256 0.0205 1.0000
9.750 1.1109 0.03580 0.02753 -0.0227 0.0182 1.0000
10.000 1.1165 0.03801 0.03000 -0.0202 0.0165 1.0000
10.250 1.1215 0.04020 0.03242 -0.0180 0.0150 1.0000
10.500 1.1245 0.04228 0.03467 -0.0161 0.0137 1.0000
10.750 1.1230 0.04462 0.03713 -0.0143 0.0124 1.0000
11.000 1.1176 0.04803 0.04071 -0.0127 0.0116 1.0000
11.250 1.1168 0.05087 0.04387 -0.0115 0.0111 1.0000
11.500 1.1123 0.05429 0.04759 -0.0106 0.0107 1.0000
11.750 1.1046 0.05820 0.05178 -0.0103 0.0105 1.0000
12.000 1.0942 0.06258 0.05644 -0.0106 0.0103 1.0000
12.250 1.0825 0.06734 0.06145 -0.0118 0.0103 1.0000
12.500 1.0683 0.07283 0.06718 -0.0139 0.0103 1.0000
12.750 1.0532 0.07890 0.07347 -0.0169 0.0102 1.0000
13.000 1.0364 0.08579 0.08057 -0.0209 0.0103 1.0000
13.250 1.0196 0.09327 0.08823 -0.0255 0.0104 1.0000
13.500 1.0021 0.10154 0.09666 -0.0308 0.0106 1.0000
13.750 0.9851 0.11033 0.10557 -0.0364 0.0107 1.0000
14.000 0.9684 0.11964 0.11498 -0.0421 0.0110 1.0000
14.250 0.9524 0.12934 0.12473 -0.0479 0.0112 1.0000
14.500 0.9390 0.13862 0.13404 -0.0530 0.0115 1.0000
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Polar data table (+)
Polar graphs
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